Performance improvement of the combat aircraft/engine unit rests on the optimization of intake/engine compatibility. This optimization requires specific flight tests in which the loss of the pumping margin of the compressors due to distortion is determined. The general methodology for the intake/engine compatibility analysis is described from the first wind tunnel tests to the flight tests. In order to determine the loss of the pumping margin due to the distortion of the air intake, an extensive instrumentation set was installed on the Mirage 2000 (Dassault Aviation) aircraft equipped with the M53-P2 (SNECMA) engine. The test procedures as well as the processing of the nonstationary signals are described. The correlations binding the nonstationary coefficients of distortion to the loss of pumping margin of the low pressure compressor are presented. It is shown that a correlation to only one parameter makes it possible to reach an accuracy of plus or minus 2 percent. On the other hand, the use of a correlation of two parameters (circumferential and radial) makes it possible to reduce the precision to plus or minus 1 percent. The use of an engine test stand in an altitude chamber with channels simulating nonstationary distortion makes it possible to reproduce in a satisfactory way the phenomena observed in flight and, in particular, to measure values of sensitivity to the distortion similar to the values obtained in flight. This method makes it possible to improve the optimization of the engine while reducing the number of flight tests.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Analyse en Vol de la Compatibilite Entree d'Air-Moteur (Flight Analysis of Air Intake/Engine Compatibility)


    Beteiligte:
    H. Joubert (Autor:in) / J. L. Eyraud (Autor:in)

    Erscheinungsdatum :

    1992


    Format / Umfang :

    12 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    SYSTEME COMPORTANT UNE ENTREE D'AIR D'UN MOTEUR D'AERONEF ET UNE PROTECTION GONFLABLE POUR LADITE ENTREE D'AIR

    CANTIN JEAN-MARC / DUBOIS OLIVIER | Europäisches Patentamt | 2021

    Freier Zugriff


    AERONEF MUNI D'UNE ENTREE D'AIR DYNAMIQUE ET D'UNE ENTREE D'AIR STATIQUE POUR ALIMENTER UN MOTEUR EN AIR

    BEDUS OLIVIER / PERRET ADRIEN / CERQUEIRA STEPHANE et al. | Europäisches Patentamt | 2019

    Freier Zugriff

    ENTREE D'AIR POUR MOTEUR D'HELICOPTERE A CIRCULATION DE CONTOURNEMENT AUGMENTEE

    JACTAT PAUL-ETIENNE / BULOT NICOLAS / LEBRUSQ PASCAL et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    ENTREE D'AIR D'UN MOTEUR D'AVION A HELICES PROPULSIVES NON CARENEES

    BENSILUM STEPHANE EMMANUEL DANIEL | Europäisches Patentamt | 2017

    Freier Zugriff